EP3414158B1 - Chaîne motrice - Google Patents

Chaîne motrice Download PDF

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Publication number
EP3414158B1
EP3414158B1 EP17707384.8A EP17707384A EP3414158B1 EP 3414158 B1 EP3414158 B1 EP 3414158B1 EP 17707384 A EP17707384 A EP 17707384A EP 3414158 B1 EP3414158 B1 EP 3414158B1
Authority
EP
European Patent Office
Prior art keywords
output shaft
front housing
drive train
housing
redundant
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP17707384.8A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP3414158A1 (fr
Inventor
Thomas Marie Joseph DE DREUILLE DE LONGEVILLE
Frédéric Nicolas François LAISNEZ
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Transmission Systems SAS
Original Assignee
Safran Transmission Systems SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Safran Transmission Systems SAS filed Critical Safran Transmission Systems SAS
Publication of EP3414158A1 publication Critical patent/EP3414158A1/fr
Application granted granted Critical
Publication of EP3414158B1 publication Critical patent/EP3414158B1/fr
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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/12—Rotor drives
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/0018—Shaft assemblies for gearings
    • F16H57/0025—Shaft assemblies for gearings with gearing elements rigidly connected to a shaft, e.g. securing gears or pulleys by specially adapted splines, keys or methods
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/02—Gearboxes; Mounting gearing therein
    • F16H57/025—Support of gearboxes, e.g. torque arms, or attachment to other devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/04—Features relating to lubrication or cooling or heating
    • F16H57/042—Guidance of lubricant
    • F16H57/0421—Guidance of lubricant on or within the casing, e.g. shields or baffles for collecting lubricant, tubes, pipes, grooves, channels or the like
    • F16H57/0424—Lubricant guiding means in the wall of or integrated with the casing, e.g. grooves, channels, holes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/02—Gearboxes; Mounting gearing therein
    • F16H2057/02039—Gearboxes for particular applications
    • F16H2057/02043—Gearboxes for particular applications for vehicle transmissions

Definitions

  • the present invention relates to a drive chain for a helicopter and a helicopter equipped with this chain.
  • a helicopter with at least one engine, which includes a cell 2 and a drive chain 3.
  • the helicopter 1 is equipped with a main rotor 11, for its lift and its propulsion and with an anti-torque tail rotor 12.
  • the drive chain 3 comprises at least one motor 4, capable of supplying mechanical power, a reduction gear 5 and a main transmission box 6 whose function is to transmit the power of this motor 4 to the two rotors, in order to drive those ci in rotation.
  • the main rotor 11 and the tail rotor 12 are rotated by two shafts, respectively referenced 61 and 62.
  • the engine 4 comprises a compressor 41, a combustion chamber 42 and turbines 43.
  • the engine 4 could also be an internal combustion engine or an electric motor.
  • the reduction gear 5 comprises a series of gears which reduce the speed of rotation of the motor shaft of the motor 4.
  • the output shaft of the reduction gear 5 is coupled to the input shaft of the main gearbox 6 so to transmit the engine torque to it.
  • the reduction gear 5 is housed inside a reduction gear housing which generally has two parts, namely a "front housing", of smaller dimensions and a “rear housing”.
  • the front casing is itself fixed to the main gearbox 6.
  • the reduction gear 5 therefore has not only a mechanical power transmission function but also a structural maintenance function of the engine 4 relative to the cell 2 of the helicopter.
  • the engine 4 is thus mounted isostatically on the helicopter 1.
  • safety standards require that the engine 4 be kept integral with the helicopter 1 and the airframe 2 thereof, in any situation, that is to say during the normal operation of the helicopter, in limit load situations (for example during a hard landing) or in ultimate load situations.
  • a flange BR having the function of attaching the engine is interposed between the main gearbox 6 and an annular flange C projecting outwards from the front casing CAV.
  • this flange BR has the shape of an annular sleeve, the front edge of which is folded outwards so as to form a front flange COAV and the rear edge of which is folded inwards so as to form a flange rear COAR.
  • This flange BR is mounted coaxially to the longitudinal axis XX ′, so that its rear flange COAR is fixed, for example referred to, to the annular flange C of the front casing CAV and that its front flange COAV is fixed, for example aimed at the wall of the main gearbox 6.
  • This BR flange is considered a critical component. It is therefore in the form of a massive piece, made of steel and oversized so as to improve its mechanical strength.
  • the invention aims to keep the engine integral with the helicopter, more precisely the main gearbox, in the event of a break in the front casing of the reduction gear, while avoiding the known drawbacks of the state of the technical.
  • the invention relates to a drive chain for a helicopter, which comprises at least one motor capable of providing mechanical power, a reduction gear and a main gearbox intended to rotate the rotor or rotors of said helicopter, the reduction gear comprising an output shaft, driven in rotation by said motor and coupled in rotation with the input shaft of said main gearbox, the reduction gear being housed in a casing in two assembled parts, called “front casing” and “rear casing ", said output shaft being supported and guided in rotation by several rolling bearings mounted in said casings.
  • this drive chain comprises a support called “redundant”, this redundant support is arranged around the output shaft and between a wall of said main gearbox and the end front of the front case, and this redundant support is configured, dimensioned and fixed to said wall of the main gearbox and to the front end of the front case, so as to create, in the event of rupture of said front case, a secondary path recovery of forces, passing through this redundant support, through the output shaft of the reducer and through said rolling bearings.
  • this redundant support is arranged around the output shaft and between a wall of said main gearbox and the end front of the front case, and this redundant support is configured, dimensioned and fixed to said wall of the main gearbox and to the front end of the front case, so as to create, in the event of rupture of said front case, a secondary path recovery of forces, passing through this redundant support, through the output shaft of the reducer and through said rolling bearings.
  • the redundant support does not take any effort when the front casing is in good condition.
  • this redundant support creates a secondary path for taking up existing forces at the front casing / main gearbox interface, and transmits these forces to the rest of the structure in particular via the reducer outlet.
  • the invention also relates to a helicopter equipped with the aforementioned drive chain.
  • the reduction gear 5 comprises an output shaft 50, driven in rotation by a motor shaft of the motor 4, not visible in these figures, and this, preferably, via a number of gears, including a pinion 54.
  • the output shaft 50 extends along a longitudinal axis XX ′. It has at the periphery of its front end, a series of grooves 51.
  • a power take-off sleeve 52 is mounted at the front end of the output shaft 50.
  • This sleeve 52 has internally a series of internal grooves 520, capable of cooperating with the grooves 51.
  • the sleeve 52 also has at its front end a peripheral front flange 521, pierced with a plurality of orifices 522.
  • the sleeve 52 is coupled to the output shaft 50 so that the splines 520 and 51 cooperate. It is retained axially in this position by a nut 53, such as a self-locking nut.
  • the rotation of the shaft 50 causes the rotation of the sleeve 52.
  • the latter can be coupled with the input shaft of the main gearbox 6, this input shaft being equipped with a sleeve similar to the sleeve 52 but not shown in the figures.
  • the two sleeves can be assembled using screws arranged through holes 522.
  • the reduction gear 5 is housed inside a casing which protects it, this casing being produced in two parts assembled to one another by suitable fixing means, namely a front casing 7 which protects the end front of the reducer, located near the main gearbox 6 and a rear casing 7 'of which only part is visible on the figure 5 .
  • the front casing 7 is more fragile, because of smaller dimensions than the rear casing 7 '.
  • the front casing 7 comprises a housing 70 for receiving the output shaft 50 of the reduction gear, of longitudinal axis XX ′.
  • a rolling bearing called "front bearing” 71, such as a ball bearing.
  • the front casing 7 has, inside the housing 70, a shoulder 72 intended to lock axially towards the rear, the outer ring 711 of said front bearing 71.
  • This front bearing 71 also includes an inner ring 712 and a plurality of balls 713.
  • the housing 70 is delimited on the front side, by a front annular edge 73 in which are tapped orifices.
  • this edge 73 comprises a plurality of ears 730, for example four in number, preferably distributed uniformly around the periphery of the edge 73.
  • the threaded orifices 731 are drilled in these ears 730.
  • the flat front face of the ears 730 and of the front edge 73 is referenced 732.
  • the front casing 7 is further provided at its periphery with a flange 74, called a "front flange”.
  • the flange 74 comprises a radial annular part 741, which is extended forward by a cylindrical part 742, then again outwards by a radial annular part 743 called "d 'end ", (see figure 5 ).
  • the cylindrical part 742 is coaxial with the axis XX '.
  • the two annular parts 741 and 743 extend in a plane perpendicular to the axis XX '.
  • the annular part 741 is set back towards the rear relative to the edge 73 of the housing 70.
  • the end portion 743 of the flange 74 is pierced right through with several orifices, namely through orifices 744, called “first fixing orifices” and blind orifices 745, called “second fixing orifices”.
  • the periphery of the end portion 743 of the flange 74 is wavy so as to define lobes around the orifices 744, 745 and narrower zones between these orifices, in order to lighten the mass of the front casing 7.
  • the end portion 743 has a flat front face 747 and an opposite rear face 746.
  • the two front faces 732 of the edge 73 and 747 of the flange 74 extend in parallel planes and preferably still distinct, the face 732 being located further back with respect to the face 747.
  • gear pinion 54 is fitted on the output shaft 50 which drives it in rotation. This fitting is achieved for example using a spline connection.
  • this gear pinion 54 is housed partly in the front casing 7 and partly in the rear casing 7 '.
  • this pinion 54 and the part of the output shaft 50 around which it is mounted are supported and guided in rotation by two rolling bearings, called “middle bearings” 75 and “rear bearing” 76, such as bearings. ball or roller.
  • the middle bearing 75 is mounted and retained inside the front casing 7 and the rear bearing 76 inside the rear casing 7 '.
  • the transmission assembly 3 comprises a redundant support 100.
  • This redundant support 100 comprises a female part 8 and a male part 9, configured to be able to be assembled.
  • the female part 8 has a generally annular shape, it is provided with a central opening 80, preferably of the same diameter as the opening of the reception housing 70 at its front annular edge 73.
  • the female part 8 has the general shape of a "deep dish", the bottom of which is pierced by the central opening 80, so as to delimit a flat inner annular crown 81.
  • the female part 8 also includes a peripheral, annular, flat outer ring 82 and between the two, an annular intermediate part 83 inclined towards the inside of the central opening 80 and towards the rear AR.
  • the inner ring 81 and the outer ring 82 thus extend in two parallel planes perpendicular to the longitudinal axis XX ′, and preferably distinct, the internal ring 81 being located more towards the rear AR than the external ring 82 .
  • the inner ring 81 is traversed right through by a plurality of fixing orifices 810, for example four in number.
  • the planar inner ring 81 has a front face 811 and an opposite rear face 812.
  • the outer ring 82 is traversed right through by a plurality of first fixing holes 821 and second fixing holes 822.
  • the edge of the outer ring 82 has a wavy shape, so as to define lobes 823 around the fixing holes 821 and 822 and narrower zones between two of these successive holes, in order to lighten the mass of the female part 8.
  • the outer ring 82 has a flat front support face 824 and a flat rear support face 825.
  • the first fixing holes 821 are intended to receive screws 84 which make it possible to assemble the female part 8 on the one hand with the flange 74 and on the other hand with the wall of the main transmission box 6.
  • the main gearbox 6 also comprises a flange 60 around its input shaft, this flange 60 being pierced with orifices 61 intended to receive the screws 84. These screws 84 cooperate with nuts 85.
  • the second fixing holes 822 allow the reception of screws 86, the end of which is intended to be received in the second fixing holes 745 of the flange 74 of the front casing 7. These screws 86 allow the crown to be fixed 82 against the part 743 of the flange 74, in particular during the disassembly of the engine, when the reduction gear is separated from the main gearbox 6. The redundant support thus remains well assembled on the reduction gear 5.
  • the inner ring 81 has a thickness E (see figure 4 ).
  • the inclined intermediate portion 83 has a drainage opening 830, preferably having the shape of a portion of an arc of a circle.
  • the female part 8 is made of aluminum.
  • the male part 9 (or “housing”) comprises a tubular part 90 delimiting a central passage 91 whose longitudinal axis is coaxial with the longitudinal axis XX 'of the output shaft 50 of the reduction gear, when this male part 9 is mounted inside the reducer.
  • the internal diameter of the central passage 91 is greater than the external diameter of the output shaft 50.
  • This male part 9 has a rear end 92 and a front end 93 (see figure 4 ).
  • the front end 93 is extended radially outwards by a flange 94.
  • This flange 94 is pierced by holes 940.
  • it has several ears 941, for example four in number, in which the holes 940 are formed.
  • the holes 940 allow the passage of screws 942 the end of which is intended to be received in the threaded holes 731 of the front housing 7 (see figure 3 ).
  • the screws 942 also pass through the fixing holes 810 of the inner ring 81 of the redundant support.
  • the flange 94 has a flat front 943 and an opposite rear face 944.
  • the male part 9 is further equipped with a rotary joint 95 comprising a fixed ring 951 and a rotary ring 952.
  • the rotary ring 952 is fitted around the output shaft 50 of the reducer. It is retained axially towards the rear, by the inner ring 712 of the front bearing 71 and towards the front, by the rear end of the PTO flange 52.
  • the tubular part of the male part 9 has internally an annular shoulder 96, which makes it possible to retain axially rearward the fixed ring 951. This is further held forwards by an elastic ring 97 received in an annular groove internal of the tubular part 90 of the male part 9.
  • the tubular part 90 of the male part 9 has in its rear part, a plurality of drainage orifices 98, which extend opposite the rotary ring 952 of the rotary joint 95. These orifices 98 make it possible to discharge the oil which could flow out of the rotary joint, in the direction of the central passage 70.
  • the opening of the drainage 830 also allows this evacuation of the oil from the rotary joint.
  • the front casing 7, the female part 8 and the male part 9 are dimensioned and configured, so that when the male part 9 is mounted on the casing 7, being screwed using screws 942, its rear end 92 comes into abutment against the outer ring 711 of the front bearing 71, while its flange 94 is spaced from the face 732 of the flange 73 of the casing 7. There is thus a space A between the rear face 944 of the flange 94 and the front face 732 of the front housing 7.
  • the length L between the rear end 92 of the male part 9 and the internal face 944 of the flange 94 is such that this space A always exists when the rear end 92 of the male part 9 is in abutment against the outer ring 711 of the front bearing 71.
  • the female part 8 and the front casing 7 are configured so that when the female part 8 is mounted, (as previously described), so that its outer peripheral ring 82 is pressed between the front casing 7 and the wall (flange 60) of the main gearbox 6, its inner ring 81 is positioned in space A and that the distance D between the rear face 944 of the flange 94 and the front face 732 of the edge 73 of the front casing 7 is greater than the thickness E of the inner ring 81.
  • the parts 7, 8 and 9 are configured so that there is always a first functional clearance j1 between the rear face 944 of the flange 94 and the front face 811 of the inner ring 81 and a second functional clearance j2 between the front face 732 of the front casing 7 and the rear face 812 of the inner ring 81.
  • the redundant support 100 then fully plays its role of emergency support and the forces are transmitted via this support 100 to the edge 73 of the front casing 7, to the front bearing 71, to the output shaft of the reducer 50 , to the pinion 54 and to the middle 75 and rear 76 bearings, these two bearings being themselves fixed to the structure by their respective outer rings.
  • the redundant support 100 also fully plays its role of emergency support and allows the creation of the alternative or secondary path for resumption of forces .

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Details Of Gearings (AREA)
EP17707384.8A 2016-02-08 2017-02-07 Chaîne motrice Active EP3414158B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1650976A FR3047471B1 (fr) 2016-02-08 2016-02-08 Chaine motrice
PCT/FR2017/050272 WO2017137690A1 (fr) 2016-02-08 2017-02-07 Chaîne motrice

Publications (2)

Publication Number Publication Date
EP3414158A1 EP3414158A1 (fr) 2018-12-19
EP3414158B1 true EP3414158B1 (fr) 2020-01-22

Family

ID=56101561

Family Applications (1)

Application Number Title Priority Date Filing Date
EP17707384.8A Active EP3414158B1 (fr) 2016-02-08 2017-02-07 Chaîne motrice

Country Status (8)

Country Link
US (1) US10875634B2 (zh)
EP (1) EP3414158B1 (zh)
JP (1) JP6930988B2 (zh)
CN (1) CN108602557B (zh)
CA (1) CA3013806A1 (zh)
FR (1) FR3047471B1 (zh)
RU (1) RU2720760C2 (zh)
WO (1) WO2017137690A1 (zh)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10851832B2 (en) * 2019-04-30 2020-12-01 Caterpillar Inc. Rotary gearbox
EP3753848B1 (en) * 2019-06-17 2021-08-04 LEONARDO S.p.A. Anti-torque rotor for a helicopter
CN114729747B (zh) 2019-09-03 2023-04-21 Sl技术有限公司 用于生物质加热系统的具有清洁装置的旋转炉排
CN111301671A (zh) * 2020-03-19 2020-06-19 常州华创航空科技有限公司 一种直升机尾推进器
US20230279938A1 (en) * 2020-09-04 2023-09-07 Sl-Technik Gmbh 3-point torque support
JP7563737B2 (ja) 2020-10-26 2024-10-08 ｅＶＴＯＬ Ｊａｐａｎ株式会社 電動ヘリコプター

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DE3708596A1 (de) * 1987-03-17 1988-09-29 Mtu Muenchen Gmbh Gasturbinenanlage fuer hubschrauber
US5203221A (en) * 1991-10-15 1993-04-20 The Falk Corporation Shaft mountable gear drive
FR2756542B1 (fr) * 1996-11-29 1999-02-12 Eurocopter France Installation de montage d'un moteur sur un plancher, et de connexion de son arbre de sortie avec au moins un mecanisme entraine
US6302356B1 (en) * 1998-08-21 2001-10-16 Rolls-Royce Corporation Helicopter two stage main reduction gearbox
US6058793A (en) * 1999-01-19 2000-05-09 Chemineer, Inc. Parallel shaft speed reducer with sump and dry well
CN101444892B (zh) * 2008-10-17 2010-12-08 电子科技大学 机械系统可重构的混联机床及其容错纠错方法
FR2952907B1 (fr) 2009-11-26 2011-12-09 Eurocopter France Installation motrice, helicoptere comportant une telle installation motrice, et procede mis en oeuvre par cette installation motrice
CN101789648B (zh) * 2009-12-30 2012-07-18 上海交通大学 冗余输入驱动器
RU2559676C2 (ru) * 2013-08-08 2015-08-10 Андрей Михайлович Трубицин Трансмиссия вертолета
FR3047053B1 (fr) * 2016-01-26 2019-07-19 Renault S.A.S Systeme d'accouplement axial d'un arbre moteur sur un arbre de transmission
US20180087639A1 (en) * 2016-09-23 2018-03-29 Bell Helicopter Textron Inc. High Speed Engine Reduction Gearboxes

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Also Published As

Publication number Publication date
CN108602557B (zh) 2021-07-16
JP2019504794A (ja) 2019-02-21
CA3013806A1 (fr) 2017-08-17
US10875634B2 (en) 2020-12-29
RU2018131314A (ru) 2020-03-10
JP6930988B2 (ja) 2021-09-01
RU2720760C2 (ru) 2020-05-13
FR3047471A1 (fr) 2017-08-11
FR3047471B1 (fr) 2018-02-16
US20190055011A1 (en) 2019-02-21
CN108602557A (zh) 2018-09-28
RU2018131314A3 (zh) 2020-04-21
WO2017137690A1 (fr) 2017-08-17
EP3414158A1 (fr) 2018-12-19

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